Aircraft engine cleaning system

ABSTRACT

A cleaning system for performing a cleaning cycle on a turbine engine mounted to an airframe includes a mobile supply unit. The mobile supply unit includes a cleaning agent supply that introduces cleaning agent into the turbine engine. The aircraft includes at least one valve configured to block cleaning agent from moving from the turbine engine into a passenger cabin of the aircraft.

CROSS REFERENCE TO RELATED APPLICATIONS

This application claims priority to and the benefit of U.S. ProvisionalPatent Application No. 62/032,751, filed Aug. 4, 2014, the disclosure ofwhich is now expressly incorporated herein by reference.

FIELD OF THE DISCLOSURE

The present disclosure relates generally to aircraft maintenance, andmore specifically to aircraft engine cleaning systems.

BACKGROUND

Aircraft engines, generally gas turbines, are periodically cleaned toremove dirt and grime from internal components of the engine. To cleanthe engines, water or another cleaning agent is introduced into theengine and the engine is dry motored (rotated without burning fuel) todraw the water over the internal components to be cleaned.

Sometimes, before introducing water into the engine, maintenance crewsmust take steps to disconnect the engines from other aircraft systems toprevent dirty water moving through the engines from escaping into theother aircraft systems. For example, crews may disconnect air supplysystems, fuel manifold systems, anti-ice systems, pressure regulationsystems, and/or controller systems before introducing water into theengine. These steps may take an inconvenient amount of time and may bedifficult to perform.

Additionally, dry motoring of aircraft engines being cleaned is oftendriven by an engine starter included in the aircraft. These enginestarters are generally limited to constant operation for only a fewminutes before they have to be rested to avoid overheating or otherdamage. Accordingly, cleaning cycles that call for extended periods ofdry motoring may take in inconvenient amount of time while the enginestarters are rested between uses. The additional time required to coolthese systems as well as the maintenance requirements for cleaning cansometimes lead to aircraft operators to defer or to cancel enginecleaning operations.

SUMMARY

The present disclosure may comprise one or more of the followingfeatures and combinations thereof.

According to the present disclosure, an aircraft may include a cabin airsystem and a gas turbine engine. The gas turbine engine may include anengine core coupled to the cabin air system to provide compressed bleedair to the cabin air system and a cleaning agent supply connectorcoupled to the engine core to conduct a cleaning agent to the enginecore.

In some embodiments, the aircraft may also include a pneumatic couplingsystem. The pneumatic coupling system may include a first valve coupledbetween the cabin air system and the engine core, a second valve coupledbetween the engine core and the cleaning agent supply connector, and acontroller coupled to the first valve. The controller may be configuredto automatically close the first valve and block compressed bleed airthat may contain cleaning agent moving through the engine core frommoving into the cabin air system in response to receipt of an inputassociated with a cleaning cycle.

In some embodiments, the controller may be coupled to the cleaning agentsupply connector and the cleaning agent supply connector may beconfigured to send the input associated with a cleaning cycle to thecontroller in response to a cleaning agent supply being coupled to thecleaning agent supply connector. The controller may be coupled to thesecond valve and the controller may be configured to automatically openthe second valve in response to receipt of the input associated with acleaning cycle.

In some embodiments, the controller may be coupled to the second valveand the second valve may be configured to send the input associated witha cleaning cycle to the controller in response to movement of the secondvalve from a closed position to an opened position.

In some embodiments, the pneumatic coupling system may include a userinterface coupled to the controller. The user interface may beconfigured to send the input associated with a cleaning cycle to thecontroller.

According to another aspect of the present disclosure, an aircraft mayinclude a cabin air system and a gas turbine engine. The gas turbineengine may be coupled to the cabin air system to provide compressedbleed air to the cabin air system.

In some embodiments, the aircraft may also include a pneumatic couplingsystem. The pneumatic coupling system may include a first valve coupledbetween the cabin air system and the gas turbine engine and a controllercoupled to the first valve. The controller may be configured toautomatically close the first valve and block compressed bleed air thatmay contain cleaning agent moving through the engine core from movinginto the cabin air system in response to receipt of an input associatedwith a cleaning cycle.

In some embodiments, the pneumatic coupling system may include a userinterface coupled to the controller. The user interface may beconfigured to send the input associated with a cleaning cycle to thecontroller.

According to another aspect of the present disclosure, a cleaning systemmay include an aircraft and a mobile supply unit. The aircraft mayinclude an airframe, a gas turbine engine coupled to the airframe, and astarter air supply coupled to the airframe. The starter air supply maybe sized to constantly dry motor the gas turbine engine for apredetermined starting cycle. The mobile supply unit may be movablerelative to the aircraft. The mobile supply unit may include a cleaningagent supply adapted to provide cleaning agent to the gas turbineengine.

In some embodiments, the mobile supply unit may also include a cleaningair supply. The cleaning air supply may be sized to provide enoughcompressed air to constantly dry motor the gas turbine engine for apredetermined cleaning cycle. The cleaning cycle may be longer than thestarting cycle.

In some embodiments, the aircraft includes a cabin air system, apneumatic coupling system, and a controller. The pneumatic couplingsystem may be coupled between a cabin air system and the gas turbineengine. The controller may be configured to automatically adjust thepneumatic coupling system to block compressed bleed air that may containcleaning agent moving through the gas turbine engine from moving intothe cabin air system in response to receipt of an input associated witha cleaning cycle.

In some embodiments, the gas turbine engine may include a cleaning agentsupply connector coupled to the cleaning agent supply by a hose and anengine core coupled to the cleaning agent supply connector to receivecleaning agent from the cleaning agent supply connector. The cleaningagent supply connector may be coupled to the controller and may beconfigured to send the input associated with a cleaning cycle to thecontroller in response to a cleaning agent supply being coupled to thecleaning agent supply connector.

In some embodiments, the pneumatic coupling system may be coupledbetween the cleaning agent supply connector and the engine core. Thecontroller may be configured to automatically adjust the pneumaticcoupling system to allow cleaning solution to move from the cleaningagent supply connector to the engine core in response to receipt of theinput associated with a cleaning cycle.

In some embodiments, the pneumatic coupling system may include a userinterface coupled to the controller. The user interface may beconfigured to send the input associated with a cleaning cycle to thecontroller.

According to another aspect of the present disclosure, a method ofcleaning an aircraft engine is taught. The method may include couplingan external cleaning air supply to a gas turbine engine included in anaircraft and introducing a cleaning agent into the gas turbine engine.

In some embodiments, the method may include dry motoring the gas turbineengine for a predetermined cleaning cycle time. This dry motoring may beperformed by conducting compressed air from the external cleaning airsupply to the gas turbine engine.

In some embodiments, the method may include coupling a cleaning agentsupply to a cleaning agent supply connector included in the gas turbineengine. The external cleaning air supply and the cleaning agent supplymay be mounted to a transport vehicle for movement together relative tothe aircraft.

In some embodiments, the aircraft may include a cabin air system, apneumatic coupling system, and a controller. The pneumatic couplingsystem may be coupled between a cabin air system and the gas turbineengine. The controller may be configured to automatically adjust thepneumatic coupling system to block compressed bleed air that may containcleaning agent moving through the gas turbine engine from moving intothe cabin air system in response to receipt of an input associated witha cleaning cycle.

In some embodiments, the cleaning agent supply connector may be coupledto the controller and may be configured to send the input associatedwith a cleaning cycle to the controller in response to a cleaning agentsupply being coupled to the cleaning agent supply connector. Thepneumatic coupling system may be coupled between the cleaning agentsupply connector and the engine core and the controller may beconfigured to automatically adjust the pneumatic coupling system toallow cleaning solution to move from the cleaning agent supply connectorto the engine core in response to receipt of the input associated with acleaning cycle.

In some embodiments, the method may include interacting with a userinterface coupled to the controller. The user interface may beconfigured to send the input associated with a cleaning cycle to thecontroller

These and other features of the present disclosure will become moreapparent from the following description of the illustrative embodiments.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a perspective view of an aircraft and a mobile supply unitused to clean turbine engines included in the aircraft;

FIG. 2 is a diagrammatic view of the aircraft and mobile supply unit ofFIG. 1 showing that a pneumatic coupling system included in the aircraftcooperates with the supply unit to provide a cleaning system;

FIG. 3 is a diagrammatic view of the aircraft and mobile supply unitsimilar to FIG. 2 showing that airframe valves controlling air flow fromthe turbine engines to an airframe included in the aircraft are openedand that a cleaning valve controlling cleaning agent flow into a core ofthe turbine engine is closed before the supply unit is coupled to theturbine engine;

FIG. 4 is a view similar to FIG. 3 showing that airframe valvescontrolling air flow from the turbine engines to the airframe areautomatically opened and that the cleaning valve controlling cleaningagent flow into the core of the turbine engine is opened in response tothe supply unit being coupled to the turbine engine;

FIG. 5 is a diagrammatic view of a first alternative aircraft and mobilesupply showing that a pneumatic coupling system included in the aircraftcooperates with the supply unit to provide a cleaning system thatcontrols airframe valves based on the state of a cleaning valve; and

FIG. 6 is a diagrammatic view of a second alternative aircraft andmobile supply showing that a pneumatic coupling system included in theaircraft cooperates with the supply unit to provide a cleaning systemthat controls a cleaning valve and airframe valves based on inputs froma user interface.

DETAILED DESCRIPTION OF THE DRAWINGS

For the purposes of promoting an understanding of the principles of thedisclosure, reference will now be made to a number of illustrativeembodiments illustrated in the drawings and specific language will beused to describe the same.

An aircraft 10 illustratively includes an airframe 12 and turbineengines 14 as shown in FIG. 1. A mobile supply unit 16 may cooperatewith the aircraft 10 to provide a cleaning system 15 used to clean theturbine engines 14 while they are mounted to the airframe 12. The mobilesupply unit 16 is illustratively configured to introduce cleaning agentinto one of the turbine engines 14 and to drive the turbine engine 14 tomove the cleaning agent through the turbine engine 14 so that internalcomponents of the turbine engine 14 are cleaned.

The mobile supply unit 16 illustratively includes a cleaning agentsupply 18 and a cleaning air supply 20 mounted to a transport vehicle 22as shown in FIG. 1. The cleaning agent supply 18 stores and providescleaning agent to the turbine engine 14. The cleaning air supply 20provides compressed air to the turbine engine 14 to drive dry motoringof the turbine engine 14, which draws cleaning agent through the turbineengine 14. For illustrative purposes, the mobile supply unit 16 is shownin the back of a truck; however, in other embodiments, the mobile supplyunit 16 may be incorporated into a work cart, trailer, or the like.

The aircraft 10 further includes a pneumatic coupling system 24 thatinterconnects the turbine engine 14 with the airframe 12 to conductpressurized air from the turbine engine 14 to the airframe 12 as showndiagrammatically in FIG. 2. In the illustrative embodiment, thepneumatic coupling system 24 is configured to pneumatically disconnectthe turbine engine 14 from the airframe 12 automatically when cleaningagent is introduced into the turbine engine 14 to block cleaning agentmoving through the turbine engine 14 from being conducted into theairframe 12 so that moisture, unpleasant odors, and grime associatedwith the cleaning agent does not enter the airframe 12. In theillustrative embodiment, the airframe 12 of the aircraft 10 includes astarter air supply 30, a cabin air system 32, and other bleed airsystems 34 as shown diagrammatically in FIG. 2. The starter air supply30 provides compressed air to the turbine engine 14 to drive short-termmotoring of the turbine engine 14 during start-up of the turbine engine14. The cabin air system 32 receives pressurized air from the turbineengine 14 and pressurizes a passenger cabin 25 of the aircraft 10. Theother bleed air systems 34 also receive pressurized air from the turbineengine 14 and use the air to perform various functions of the airframe12. Examples of other bleed air systems 34 include air supply systems,fuel manifold systems, anti-ice systems, pressure regulation systems,and controller systems.

The turbine engines 14 provide thrust for the aircraft 10 and eachillustratively includes an engine core 40, a supply connector 42, and afan 44 as shown in FIG. 2. The engine core 40 burns fuel to drive thefan 44 and includes a compressor (not shown) from which pressurized airis bled off to supply the cabin air system 32 and the other bleed airsystems 34. The supply connector 42 is adapted to be coupled to thecleaning agent supply 18 and is configured to conduct cleaning agentinto the engine core 40. The supply connector 42 is illustrativelyarranged between the engine core 40 and the fan 42 so that cleaningagent introduced into the engine core 40 does not have to pass over thefan 44 such that the fan 44 might push some cleaning agent away frommoving into the engine core 40. The fan 44 accelerates atmospheric airinto and around the engine core 40 to create thrust.

The pneumatic coupling system 24 included in the aircraft 10illustratively includes a cleaning valve 50, a bleed air manifold 52,and a controller 54 as shown diagrammatically in FIG. 2. The cleaningvalve 50 is illustratively coupled pneumatically between the engine core40 and the supply connector 42 to block or allow cleaning agent movementinto the engine core 40 from the supply connector 42. The bleed airmanifold 52 is illustratively coupled pneumatically between the enginecore 40 and the airframe 12 to block or allow pressurized air movementinto the airframe 12 from the engine core 40. The controller 54 iscoupled to the cleaning valve 50, the bleed air manifold 52, and to thesupply connector 42 to control the cleaning valve 50 and the bleed airmanifold 52 based on inputs from the supply connector 42. In someembodiments, the pneumatic coupling system 24 may be wholly or partiallyintegrated into the turbine engine 14 and/or the airframe 12.

The bleed air manifold 52 illustratively includes a first airframe valve56 and a second airframe valve 58 as shown in FIG. 2. The first airframevalve 56 is coupled pneumatically between the engine core 40 and thecabin air system 32 to block or allow pressurized air from the enginecore 40 into the cabin air system 32. The second airframe valve 58 iscoupled pneumatically between the engine core 40 and the other bleed airsystems 34 to block or allow pressurized air from the engine core 40into the other bleed air systems 34.

The controller 54 illustratively includes a processor 60 and memory 62coupled to the processor 60 as shown in FIG. 2. The processor 60 is ofany suitable type and is configured to execute instructions stored inthe memory 62. The memory 62 is illustratively of any suitable type andcontains instructions associated with the operation of the cleaningvalve 50 along with the airframe valves 56, 58 included in the air bleedmanifold 52.

Based on illustrative instructions stored in the memory 62, thecontroller 54 is configured to close both the first and the secondairframe valves 56, 58 and to open the cleaning valve 50 automaticallyahead of a cleaning cycle as suggested in FIG. 4. More specifically, thecontroller 54 is configured to close both the airframe valves 56, 58 andto open the cleaning valve 50 in response to receiving a signalassociated with a cleaning cycle. Accordingly, during a cleaning cycle,both the first airframe valve 56 and the second airframe valve 58 blockmovement of cleaning agent and pressurized air from the turbine engine14 into the airframe 12.

In the illustrative embodiment, the controller 54 receives the signalassociated with the cleaning cycle from the supply connector 42 uponconnection of the cleaning agent supply 18 to the supply connector via ahose 17. In other embodiments, the cleaning cycle signal may begenerated by other devices that may be connected to the controller 54.

Further, based on the instructions stored in the memory 62, thecontroller 54 is configured to open both the first and the secondairframe valves 56, 58 and to close the cleaning valve 50 automaticallyafter a cleaning cycle. More specifically, the controller 54 isconfigured to open both the airframe valves 56, 58 and to close thecleaning valve 50 in response to receiving a signal associated withnormal operation of the aircraft 10. Accordingly, during normaloperation of the aircraft 10, both the first airframe valve 56 and thesecond airframe valve 58 allow pressurized air from the turbine engine14 into the airframe 12.

In the illustrative embodiment, the controller 54 receives the signalassociated with normal operation from the supply connector 42 upondisconnection of the cleaning agent supply 18 from the supply connector.In other embodiments, the normal operation signal may be generated byother devices that may be connected to the controller 54.

The starter air supply 30 is internal to the aircraft 10 and isillustratively sized to constantly dry motor the turbine engine 14 for apredetermined starting cycle of about one (1) minute to five (5) minutesas needed during startup of the turbine engines 14. After thepredetermined starting cycle, the starter air supply 30 requires anillustrative recharging or cooling period of about thirty (30) minutesto forty-five (45) minutes.

The cleaning air supply 20 is external to the aircraft 10 and coupled tothe engine core 40 by a hose 19 as shown in FIG. 1. The cleaning airsupply 20 is illustratively sized to constantly dry motor the turbineengine 14 for a predetermined cleaning cycle of about thirty (30)minutes to ninety (90) minutes as needed during cleaning of the turbineengines 14. The ability of the cleaning air supply 20 to dry motor theturbine engine 14 for the entire cleaning cycle without recharging orcooling may allow the total time required for engine cleaning to bereduced.

In the illustrative embodiment, the cleaning agent supply 18 isconfigured for use with foamed cleaning agents available from MatrixScientific and Aerocore Technologies, both of Columbia, S.C., U.S.A. Inother embodiments, the cleaning agent supply 18 may be used with othercleaning agents such as, in one example, deionized water. Additionally,the cleaning agent supply 18 may be used to conduct cleaning agent ontothe fan 44 while the turbine engine 14 is dry motored to clean the fan44. Cleaning agent may be sprayed onto the fan 44 from the cleaningagent supply 18 by a wand (not shown) before, during, and/or afterintroduction of cleaning agent directly into the engine core 40 throughthe supply connector 42 as part of a cleaning cycle.

Another illustrative controller 255 integrated into the pneumaticcoupling system 24 of the aircraft 10 is shown diagrammatically in FIG.5. The controller 255 illustratively includes a processor 260 and memory262 coupled to the processor 260 as shown in FIG. 5. The processor 260is of any suitable type and is configured to execute instructions storedin the memory 262. The memory 262 is illustratively of any suitable typeand contains instructions associated with the operation of the cleaningvalve 50 along with the airframe valves 56, 58 included in the air bleedmanifold 52

Unlike the controller 54, the controller 255 is not coupled to a supplyconnector 242 to receive signals associated with a cleaning cycle ornormal operation from the supply connector. Rather, the controller 255receives signals associated with the cleaning cycle or normal operationfrom the cleaning valve 50.

Based on illustrative instructions stored in a memory 263 included inthe controller 255, the controller 255 is configured to close both thefirst and the second airframe valves 56, 58 and to open the cleaningvalve 50 automatically ahead of a cleaning cycle in response toreceiving a signal associated with the cleaning cycle from the cleaningvalve 50. Illustratively, the controller 54 receives the signalassociated with the cleaning cycle from the cleaning valve 50 uponopening of the cleaning valve 50. Accordingly, during a cleaning cycle,both the first airframe valve 56 and the second airframe valve 58 blockmovement of cleaning agent and pressurized air from the turbine engine14 into the airframe 12.

Further, based on the instructions stored in the memory 62, thecontroller 255 is configured to open both the first and the secondairframe valves 56, 58 and to close the cleaning valve 50 automaticallyafter a cleaning cycle in response to receiving a signal associated withnormal operation from the cleaning valve 50. Illustratively, thecontroller 54 receives the signal associated with normal operation fromthe cleaning valve 50 upon closing of the cleaning valve 50.Accordingly, during normal operation of the aircraft 10, both the firstairframe valve 56 and the second airframe valve 58 allow pressurized airfrom the turbine engine 14 into the airframe 12.

Another illustrative controller 355 integrated into the pneumaticcoupling system 24 of the aircraft 10 is shown diagrammatically in FIG.5. The controller 355 illustratively includes a processor 360 and memory362 coupled to the processor 360 as shown in FIG. 6. The processor 360is of any suitable type and is configured to execute instructions storedin the memory 362. The memory 362 is illustratively of any suitable typeand contains instructions associated with the operation of the cleaningvalve 50 along with the airframe valves 56, 58 included in the air bleedmanifold 52.

Unlike the controller 54, the controller 355 is not coupled to a supplyconnector 242 to receive signals associated with a cleaning cycle ornormal operation from the supply connector. Rather, the controller 355receives signals associated with the cleaning cycle or normal operationfrom a user interface 375. The user interface 375 may be button, aswitch, a knob, a graphical user interface, or any other suitable inputin communication with the controller 355. In some versions of thisembodiment, the supply connector 42 and the cleaning valve 50 may beomitted and a wand may be used to introduce cleaning agent into theturbine engine 14.

Based on illustrative instructions stored in memory 362 included in thecontroller 355, the controller 355 is configured to close both the firstand the second airframe valves 56, 58 and to open the cleaning valve 50automatically ahead of a cleaning cycle in response to receiving asignal associated with the cleaning cycle from the cleaning valve 50.Illustratively, the controller 54 receives the signal associated withthe cleaning cycle from the user interface 375 upon a firstpredetermined input from a user being detected by the user interface375. Accordingly, during a cleaning cycle, both the first airframe valve56 and the second airframe valve 58 block movement of cleaning agent andpressurized air from the turbine engine 14 into the airframe 12.

Further, based on the instructions stored in memory 362, the controller355 is configured to open both the first and the second airframe valves56, 58 and to close the cleaning valve 50 automatically after a cleaningcycle in response to receiving a signal associated with normal operationfrom the cleaning valve 50. Illustratively, the controller 54 receivesthe signal associated with normal operation from the user interface 375upon a second predetermined input from a user being detected by the userinterface 375. Accordingly, during normal operation of the aircraft 10,both the first airframe valve 56 and the second airframe valve 58 allowpressurized air from the turbine engine 14 into the airframe 12.

While the disclosure has been illustrated and described in detail in theforegoing drawings and description, the same is to be considered asexemplary and not restrictive in character, it being understood thatonly illustrative embodiments thereof have been shown and described andthat all changes and modifications that come within the spirit of thedisclosure are desired to be protected.

What is claimed is:
 1. An aircraft comprising a cabin air system, a gasturbine engine including an engine core coupled to the cabin air systemto provide compressed bleed air to the cabin air system and a cleaningagent supply connector coupled to the engine core to conduct a cleaningagent to the engine core, and a pneumatic coupling system including afirst valve coupled between the cabin air system and the engine core, asecond valve coupled between the engine core and the cleaning agentsupply connector, and a controller coupled to the first valve, thecontroller configured to automatically close the first valve and blockcompressed bleed air that may contain cleaning agent moving through theengine core from moving into the cabin air system in response to receiptof an input associated with a cleaning cycle.
 2. The aircraft of claim1, wherein the controller is coupled to the cleaning agent supplyconnector and the cleaning agent supply connector is configured to sendthe input associated with a cleaning cycle to the controller in responseto a cleaning agent supply being coupled to the cleaning agent supplyconnector.
 3. The aircraft of claim 2, wherein the controller is coupledto the second valve and the controller is configured to automaticallyopen the second valve in response to receipt of the input associatedwith a cleaning cycle.
 4. The aircraft of claim 1, wherein thecontroller is coupled to the second valve and the second valve isconfigured to send the input associated with a cleaning cycle to thecontroller in response to movement of the second valve from a closedposition to an opened position.
 5. The aircraft of claim 1, wherein thepneumatic coupling system includes a user interface coupled to thecontroller and the user interface is configured to send the inputassociated with a cleaning cycle to the controller.
 6. A cleaning systemcomprising an aircraft including an airframe, a gas turbine enginecoupled to the airframe, and a starter air supply coupled to theairframe, the starter air supply sized to constantly dry motor the gasturbine engine for a predetermined starting cycle, and a mobile supplyunit movable relative to the aircraft, the mobile supply unit includinga cleaning agent supply adapted to provide cleaning agent to the gasturbine engine and a cleaning air supply sized to provide enoughcompressed air to constantly dry motor the gas turbine engine for apredetermined cleaning cycle, the cleaning cycle being longer than thestarting cycle.
 7. The cleaning system of claim 6, wherein the aircraftincludes a cabin air system, a pneumatic coupling system, and acontroller, the pneumatic coupling system coupled between a cabin airsystem and the gas turbine engine, and the controller configured toautomatically adjust the pneumatic coupling system to block compressedbleed air that may contain cleaning agent moving through the gas turbineengine from moving into the cabin air system in response to receipt ofan input associated with a cleaning cycle.
 8. The cleaning system ofclaim 7, wherein the gas turbine engine includes a cleaning agent supplyconnector coupled to the cleaning agent supply by a hose and an enginecore coupled to the cleaning agent supply connector to receive cleaningagent from the cleaning agent supply connector.
 9. The cleaning systemof claim 8, wherein the cleaning agent supply connector is coupled tothe controller and is configured to send the input associated with acleaning cycle to the controller in response to a cleaning agent supplybeing coupled to the cleaning agent supply connector.
 10. The aircraftof claim 9, wherein the pneumatic coupling system coupled between thecleaning agent supply connector and the engine core and the controlleris configured to automatically adjust the pneumatic coupling system toallow cleaning solution to move from the cleaning agent supply connectorto the engine core in response to receipt of the input associated with acleaning cycle.
 11. The aircraft of claim 8, wherein the pneumaticcoupling system includes a user interface coupled to the controller andthe user interface is configured to send the input associated with acleaning cycle to the controller.
 12. A method of cleaning an aircraftengine, the method comprising coupling an external cleaning air supplyto a gas turbine engine included in an aircraft; introducing a cleaningagent into the gas turbine engine; and dry motoring the gas turbineengine for a predetermined cleaning cycle time by conducting compressedair from the external cleaning air supply to the gas turbine engine. 13.The method of claim 12 further comprising coupling a cleaning agentsupply to a cleaning agent supply connector included in the gas turbineengine.
 14. The method of claim 13, wherein the external cleaning airsupply and the cleaning agent supply are mounted to a transport vehiclefor movement together relative to the aircraft.
 15. The method of claim13, wherein the aircraft includes a cabin air system, a pneumaticcoupling system, and a controller, the pneumatic coupling system coupledbetween a cabin air system and the gas turbine engine, and thecontroller is configured to automatically adjust the pneumatic couplingsystem to block compressed bleed air that may contain cleaning agentmoving through the gas turbine engine from moving into the cabin airsystem in response to receipt of an input associated with a cleaningcycle.
 16. The method of claim 15, wherein the cleaning agent supplyconnector is coupled to the controller and is configured to send theinput associated with a cleaning cycle to the controller in response toa cleaning agent supply being coupled to the cleaning agent supplyconnector.
 17. The method of claim 16, wherein the pneumatic couplingsystem coupled between the cleaning agent supply connector and theengine core and the controller is configured to automatically adjust thepneumatic coupling system to allow cleaning solution to move from thecleaning agent supply connector to the engine core in response toreceipt of the input associated with a cleaning cycle.
 18. The method ofclaim 15, further comprising interacting with a user interface coupledto the controller, wherein the user interface is configured to send theinput associated with a cleaning cycle to the controller.